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Research on measurement and control of helicopter rotor response using blade-mounted accelerometers 1991-92Preliminary wind tunnel tests of the hill-size Model 412/IBC rotor at the Ames Research Center, NASA, are described. Blade flapping motion was excited by swash plate oscillation, and the flapping response was measured using blade-mounted accelerometers and compared with flapping motion inferred form blade strain measurements. The recorded open-loop accelerometer signals were used as input to the flapping-IBC system in the laboratory. The resulting controller cyclic pitch outputs are compared with the original cyclic pitch excitation inputs, and the potential effectiveness of the controller in suppressing the original excitation is evaluated. Control of blade flapping excites blade lagging, and vice versa; the paper describes a theoretical investigation of these coupling effects.
Document ID
19940035463
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ham, Norman D.
(MIT Cambridge, MA, United States)
Mckillip, Robert M., Jr.
(Continuum Dynamics, Inc. Princeton, NJ, United States)
Date Acquired
August 16, 2013
Publication Date
September 1, 1992
Subject Category
Aircraft Stability And Control
Accession Number
94A12118
Funding Number(s)
CONTRACT_GRANT: NCC2-366
Distribution Limits
Public
Copyright
Other

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